Turbine engine having an element for deflecting foreign objects

Abstract

A turbine engine having a nacelle is provided. The nacelle includes, upstream, an air intake fairing and an element for deflecting foreign objects which defines with the fairing an air intake flow path for supplying air to two coaxial flow paths which are a radially inner flow path and a radially outer flow path. The outer flow path being is by a hub housing and scoops, the hub housing and the scoops being installed downstream of the element for deflecting objects. Each scoop includes two independent portions which are an upstream portion borne by the hub housing, and a downstream portion borne by the nacelle.

The invention claimed is: 
     
       1. A turbine engine comprising:
 a nacelle comprising, at an upstream end, an air intake fairing and a deflection element which deflects foreign objects, the air intake fairing and the deflection element defining an air intake flow path for supplying air to two coaxial flow paths which are a radially inner flow path and a radially outer flow path, said outer flow path being defined by a hub housing and scoops, said hub housing and said scoops being fitted downstream of the deflection element, 
 wherein the hub housing comprises a hub and an outer collar extending outside the hub and coaxial with the hub, the outer collar being connected to the hub by radial arms of the hub housing, 
 wherein an upstream portion of the outer flow path is defined by the hub and the outer collar, 
 wherein each scoop comprises an inner cylindrical wall, an outer cylindrical wall, and two lateral walls connecting the inner cylindrical wall and the outer cylindrical wall, the inner cylindrical wall extending downstream and outward in continuation of the hub, and the outer cylindrical wall extending downstream and outward in continuation of the outer collar, 
 wherein each scoop comprises an upstream portion attached to the hub housing and a downstream portion attached to the nacelle, the upstream portion and the downstream portion being independent and separable from each other, 
 wherein a downstream end of the upstream portion includes an outlet, and an upstream end of the downstream portion includes an inlet, the outlet of the upstream portion and the inlet of the downstream portion each being delimited by the inner cylindrical wall, the outer cylindrical wall, and the two lateral walls such that shapes of the outlet of the upstream portion and the inlet of the downstream portion are the same, and 
 wherein the upstream portion of each scoop is cantilevered to a downstream end of the hub housing, the downstream portion of each scoop is rigidly attached to a movable cowl of the nacelle, and in a first open position of the cowl, the downstream end of the upstream portion and the upstream end of the downstream portion are not in fluid communication with each other, and in a second closed position of the cowl, the downstream end of the upstream portion and the upstream end of the downstream portion abut each other so as to be in fluid communication with each other. 
 
     
     
       2. The turbine engine according to  claim 1 , wherein a seal is installed between the upstream and downstream portions of each scoop. 
     
     
       3. The turbine engine according to  claim 2 , wherein the seal of each scoop includes a joint which is compressed upon installation between a downstream peripheral edge of the upstream portion and an upstream peripheral edge of the downstream portion. 
     
     
       4. The turbine engine according to  claim 3 , wherein the upstream and downstream portions of each scoop are installed substantially end to end in a sealing plane which forms a non-zero angle with a plane perpendicular to a longitudinal axis of the turbine engine. 
     
     
       5. The turbine engine according to  claim 1 , wherein an air/oil heat exchanger is installed in the nacelle and comprises an air circuit supplied by an outlet of at least one of the scoops. 
     
     
       6. The turbine engine according to  claim 1 , comprising three scoops being spaced apart and uniformly distributed about a longitudinal axis of the turbine engine. 
     
     
       7. The turbine engine according to  claim 1 , wherein one of the upstream and downstream portions of the scoop includes a seal configured for compression between the upstream and downstream portions in the second closed position of the cowl. 
     
     
       8. The turbine engine according to  claim 1 , wherein the lateral walls extend downstream in continuation of two adjacent radial arms of the hub housing.